A lifting-surface solution for vortex-induced airloads
Loads induced on infinite aspect ratio wing by straight infinite free vortex in subsonic compressible freestream, using planar lifting surface theory
Johnson, W.↗
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A method for predicting helicopter wake geometry, wake-induced flow and wake effects on blade airloads
Wake model and computer program to compute geometries, flows and velocity influence coefficients for helicopter blade load calculations
Sadler, S. G.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot unitary plan wind tunnel for Mach range 0.6 to 1.4 (IA14A), Volume 2
Results of tests conducted on an 0.030-scale launch configuration model of the space shuttle vehicle 140A/B in the NASA/ARC 11-foot unitary plan wind tunnel are presented. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 1.4. Surface pressure distributions were obtained simultaneously with six-component stability and control force data on the complete launch configuration. The configuration consisted of the orbiter, an external tank, two solid rocket boosters, and associated intercomponent attach hardware. Angles of attack and sideslip from -10 degrees to +10 degrees were investigated.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot unitary plan wind tunnel for Mach range 0.6 to 1.4 (IA14A), volume 1
The results of the tests are presented along with aerodynamic loads data obtained at Mach numbers from 0.6 to 1.4. Surface pressure distributions were obtained simultaneously with six-component stability and control force data on the complete launch configuration. The configuration consisted of the orbiter, an external tank, two solid rocket boosters, and associated intercomponent attach hardware. Angles of attack and sideslip from -10 deg to +10 deg were investigated. The tests were conducted from 4 September 1973 through 13 September 1973.
Gillins, R. L.↗
Airloads investigation of an 0.030 scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 9 by 7 foot unitary plan wind tunnel for Mach 1.55 and 2.2 (iA14B), volume 1
Tests were conducted in September, 1973 on a launch vehicle configuration consisting of a space shuttle orbiter, an external tank, two solid rocket boosters, and associated intercomponent attach hardware. Model variables included elevon, rudder, and speed brake deflections. Aerodynamic loads were measured and surface pressure distributions were obtained simultaneously with six-component stability and control force data on the complete configuration. Angles of attack and sideslip were also investigated.
Gillins, R. L.↗
Airloads investigation of an 0.30-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 5
Pressure data are presented in tabular form on the lower wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 6
Pressure data are presented in tabular form on the upper wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030 scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 7
Pressure data are presented in tabular form on the left and right vertical tail surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 8
Pressure data are presented in tabular form on the SRM booster of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 9
Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the Space Shuttle Vehicle 140 A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for MACH range 0.6 to 1.4 (IA14A), volume 10
Pressure data are presented in tabular form on the external tank base and SRM booster base of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 11
Pressure data are presented in tabular form on the external tank attach points and the external tank base rake of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
Gillins, R. L.↗
Airloads near the open port of a one-meter airborne telescope
An infrared telescope is mounted in a cavity in the fuselage of a C-141 airplane. The cavity is sealed off from the rest of the fuselage and can be opened to the outside for viewing. A retractable porous spoiler is installed ahead of the opening to inhibit cavity resonance. The paper presents the mean pressures, pressure fluctuations, spectra, phase, and coherence of the pressures in the cavity and on the fuselage near the cavity, along with pertinent acceleration and torque information for the aircraft structure and telescope. It is shown that a moderate spoiler extension controls resonance in normal flight attitudes and produces a cavity environment with approximately the same turbulence intensity as an attached turbulent boundary layer.
Buell, D. A.↗
Investigation of rotor blade element airloads for a teetering rotor in the blade stall regime (second wind tunnel test)
A test was conducted in the NASA-Ames 7 x 10 ft low speed wind tunnel on a seven-foot diameter model of a teetering rotor. The objectives of the test were: (1) acquire pressure data for correlation with laser and flow visualization measurements; (2) explore rotor propulsive force limits by varying the advance ratio at constant lift and propulsive force coefficients; (3) obtain additional data to define the differences between teetering and articulated rotors; and (4) verify the acceleration sensitivity of experimental transducers. Results are presented.
Dadone, L. U.↗
A numerical method for the exact calculation of airloads associated with impulsively started wings
A numerical method is developed to calculate three-dimensional potential flows due to the steady and impulsive motion of isolated wing and wing-wing interaction problems. The velocity potential is represented by a discrete set of constant-doublet quadrilaterals on wing and wake surfaces. The exact surface boundary condition is enforced, and the solution is obtained in a step-by-step fashion, configurations being impulsively started from rest. Free-wake geometries are generated for each time step with Rankine or Lamb viscous vortex segments used in wake-velocity calculations. Sample results include calculated performance to steady state for a thick wing and indicial lift of a wing-wing interaction problem.
Summa, J. M.↗